Directional controlling means for aircraft



Jan. 13, 1931. H. JUNKERs DIREGTIONAL coN'rRoLLlNG lmums PoR Arncnm Filed Jan. 4. 1929 tamed Jan. 13, 1931 'd d 1,788,836

STATES PA'vrisNTjoFFlcrzx;vv

Application ed January 4, 1929, Serial No. 330,332and in Germany January 16,1928. 'n

My invention refers to directional control-v tin, a rudder and afniechanism yfor operating lin means for aircraft and moreespecially the fin andthe rudder, f l f y ,y ilying machines and has for one of its objects Fig. 2 is a plainview of an airplane towhich to provide means whereby the o eration of the fin and rudder'are fitted. y p j 5 such controlling means is facilltated and Referringnow to the drawings, 1 is the fin 55 rendered more efficient and reliable. which is pivoted on the `fuselage of the air- In the drawings aiiixed to this speciicaplane at'3z y2is the rudder, 4 is its pivotal contion and forming part thereof a great numnectionwith4 the fin, 5 is anarm on the fin, 6 ber of different modifications of a directional is a control rod which is linked to the arm Y5 f 10 controlling means applied to an aircraft em at 55.` 62 is an arm on the rudder 2,and 65v 60 bodyinkriny invention is illustrated diagramis a rod which is pivotally connected with the maticallyby way of example. arm 62 at its `end 68 while its other endr 66 'isy Directional controlling means as a rule conpivoted to a part on the rod 6, for instance a Asiste ofla fin or dampin surface and a rudnut 56 which is adapted to be displaced on 15 der arranged immediate y at the rear of the the threaded end 57 of the rod 6 by means of 65 fin. It has already been suggested to rock a hand wheel 58. The point 66 is far in adnot only the rudder but also the `fin in .the jvance of the pivot 3 of the fin, and also of its same direction so that the angle through arm 5. When the rod 6 is moved the oint which the rudder moves with respect to the 63 of thearm 62 on the rudder 2 descri es a gn axis of the system, is larger than the angle curve resulting from the lon 'tudinal dis 70 `through which the fin moves. It has also placement of the point 66 an the rocking been suggested. to arrange the fixed pivot of movement of the` pivot 4. the 1in outside the pivot of the rudder so A is the axis or neutral line of the system. `that the pivot of the rudder moves bodily In the initial position the pivots 3 and .4 and g5 with the fin. the trailing e e of the rudder 2 are all in 'ns My invention relates to directional controlthe line A. W en the fin 1 isrocked to the ling means of the last-mentioned type and its left as shown in Fig. 1k the rudder is also principal object is to provide mechanism rocked about its pivot 4 but to a larger angle. y which, notwithstanding its great simplicity, The neutral positionof the s stem can herev 30 effects by positive means the desired diierbe varied by displacing the llnk point 66 on 80 .ential displacement of the fin and the ruddei' the rod or wire. y

In reducing my invention to practice I Referring now to Fig.,2, 7 is the fuselage prefer providing an arm on the rudder which of an airplane, 8 and 9 are its wings, 10 is projects from the sidethereof, and I connect the cockpit and 11 is the propeller.

,g5 the end of this arm with one end of a rod, 12 is a control rodpwhich extends from the 85 the other end of which is connected with the cockpit to the rear of the fusela e 7 13 is a main control at a point far in advance of the double-armed lever on the fuse age to one pivot of the fin. arm of which the rod 12 is hingedat 14, the

. f The pivotof the rudder may be arran ed rod 6 bein hinged to its other arm at `15.

4c at the rear end of the fin or at any'point e- 16 is a orizontal stabilizery at the end of 90 tween the rear end` and the pivot of the fin the fuselage and 17is an elevator. without departing from my invention. I wish 1t to be understood that I do not The art which is ivoted to the fin has 'desire to be limitedr to the exact details of been re erred to as t e rudder but it is to construction shown and described for obvi- 'as be understood that I am not limited to rudous modifications will .occur to -a person 95 ders but that my invention may also be apskilled-in the art.V f plied to elevators without departing therevIn the claims affixed to this specification Jgeom, no selection of any particular modification o In the drawings@- y e of the invention is intended to the exclusion so Fig. l is a partly sectional elevation of a of other modifications thereofy and the right 10o to subsequently make claim to any modiica tion not covered by these claims is expressly reserved.

I claim 5 1. In an aircraft in combination,` a damping iin mounted for rocking movement, a surface pivotally connected with said iin at a point outside the point about which said iin rocks, an arm extending from said tin, 'a control rod linked to said arm, an arm extending from sai-d surface, and a rod extendin from said arm on said surface. to said contro rod and connected to said rod at a point far in advance of the point about which said fin rocks.

2. In an aircraft in combination, a damping fin mounted for rocking movement, a surface pivotally connected with said fin at a point outside the point about Which said tin 2o rocks, an arm extending from said n, a control rod linked to said arm, an arm extending from said surface, a rod extending from said arm on said surface to said control rod and connectedto said, rod at a point far in ad- Vance of the point kabout which said fin rocks, and means for varying the position of said connecting point on said control rod.`

In' testimony whereof I aix my signature.

3 HUGO JUNKERS. 

